CN103912577A - Split-type turbocharger thrust bearing - Google Patents
Split-type turbocharger thrust bearing Download PDFInfo
- Publication number
- CN103912577A CN103912577A CN201310743167.2A CN201310743167A CN103912577A CN 103912577 A CN103912577 A CN 103912577A CN 201310743167 A CN201310743167 A CN 201310743167A CN 103912577 A CN103912577 A CN 103912577A
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- Prior art keywords
- thrust bearing
- oil
- face
- bearing
- oil film
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C17/00—Sliding-contact bearings for exclusively rotary movement
- F16C17/04—Sliding-contact bearings for exclusively rotary movement for axial load only
- F16C17/047—Sliding-contact bearings for exclusively rotary movement for axial load only with fixed wedges to generate hydrodynamic pressure
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C2360/00—Engines or pumps
- F16C2360/23—Gas turbine engines
- F16C2360/24—Turbochargers
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- Supercharger (AREA)
Abstract
The invention belongs to the field of turbochargers and relates to a split-type turbocharger thrust bearing. The split-type turbocharger thrust bearing comprises a main thrust bearing arranged at a turbocharger compressor end and a supplementary thrust bearing close to a turbine end. The main thrust bearing and the supplementary thrust bearing are coaxially arranged at the end of a turbine shaft and respectively fit to two end surfaces of a shaft seal gasket. A fan-shaped oil wedge surface is arranged on the end surface of the main thrust bearing. The end of the fan-shaped oil wedge surface is provided with an oil storage groove. The fan-shaped oil wedge surface radially forms an inclined plane rising from the circle center to exterior and circumferentially forms an inclined plane rising or dropping. The radial periphery of the fan-shaped oil wedge surface and the end surface of the main thrust bearing are aligned and form a radial oil sealed edge. The raised edge of the circumferential inclined plane of the fan-shaped oil wedge surface and the end surface of the main thrust bearing are aligned so that a circumferential oil sealing edge is formed. The split-type turbocharger thrust bearing improves a bearing bearing capacity and reduces a mechanical loss of the turbocharger bearing by about 30%. Based on an increasing rate of engine boost pressure, turbo-lag is shortened by 6-10%.
Description
Technical field
The invention belongs to field of turbochargers, specifically a kind of split type thrust bearing of turbocharger.
Background technique
In recent years, due to municipal pollution and noise nuisance more and more serious, various countries' environmental legislation control is more and more stricter, has promoted the development of the petrol engine such as minibus and passenger car turbocharging technology.Petrol engine air admission supercharging technology is the developing history of existing over half a century almost, but a very long road has but been experienced in its development.Main cause is exactly that diesel engine and petrol engine work characteristics separately exist very big difference, particularly on the formation of mixed gas and combustion manner, boost performance is had to great impact, makes petrol engine air admission supercharging more a lot of than diesel engine supercharging difficulty technically.
For petrol engine, after supercharging, improve the temperature and pressure of the interior mixed gas compression of cylinder and combustion gas, increase the heat load of firing chamber Heating Components, be easy to produce pinking, thereby mechanical property, the greasy property etc. of motor are all affected.Petrol engine delivery temperature is higher than diesel engine in addition, and the rotating ratio diesel engine of petrol engine is high, and air mass flow changes larger.All the material to turbocharger for gasoline engine and parts thereof, design, manufacture and processing are had higher requirement for these.
In vehicle turbocharger design, the design of thrust bearing is extremely important, and it not only directly affects reliability and the working life of supercharger structure, and thrust bearing accounts for the major part of bearing power loss, also can affect the efficiency of turbosupercharger.In all faults of pressurized machine, the fault causing due to bearing (thrust bearing and floating bearing) accounts for 40% left and right according to statistics.And in bearing fault, the rate of fault of thrust bearing is again higher than floating bearing.Once thrust bearing damages, and directly causes impeller and housing grazing, rotor is stuck, and pressurized machine quits work.Therefore,, in order to improve the reliability of turbocharger for gasoline engine of new generation, development and development of new thrust bearing are imperative.
The thrust bearing tow sides of turbosupercharger all need to have very high bearing capacity, and monolithic thrust bearing need to form two oil pockets at positive and negative, thereby consumes a large amount of lubricant oil, conventionally accounts for the more than 70% of whole turbosupercharger fuel delivery.
Summary of the invention
The problem to be solved in the present invention is to provide the split type thrust bearing of turbocharger that a kind of lubrication oil consumption is few.
The present invention has adopted following technological scheme:
Split type thrust bearing of turbocharger, it comprises is located at the main thrust bearing of supercharger air compressor end and the secondary thrust bearing near turbine end, main thrust bearing is located at the end of turbine shaft and is fitted in two end face settings of shaft seal pad with secondary thrust bearing is concentric, the end face of main thrust bearing is provided with fan-shaped oil film wedge face, the end of oil film wedge face is provided with oil storage tank, oil film wedge face diameter, to outwards forming by the center of circle inclined-plane increasing, is circumferentially the inclined-plane that successively decreases or increase progressively; Oil film wedge face diameter to outer rim and the end face of main thrust bearing form radially oil sealing limit, the raised limit of oil film wedge face circumferential ramps and the end face of main thrust bearing form circumferential oil sealing limit.
The end face of described secondary thrust bearing is provided with space curved surface oil film wedge face.
Advantage of the present invention is to have improved bearing capacity, on two bearings, respectively have an oil film wedge face, and two oil film wedge faces assemble in opposite directions, form a lubricant reservoir, so its fuel delivery almost can reduce half, make the mechanical loss of turbo-charger bearing lower approximately 30%.Climbing speed with engine boost pressure is weighed, and turbo lag can shorten 6%～10%.Meanwhile, owing to being split type bearing, can, effectively according to the size of pressurized machine different direction bearing capacity, accurately design respectively the structure of two thrust bearings, to reduce to greatest extent abrasion loss.
Accompanying drawing explanation
Fig. 1 is mounting structure schematic diagram of the present invention;
Fig. 2 is the structural representation of main thrust bearing;
Fig. 3 is the structural representation of secondary thrust bearing;
Fig. 4 is oil film wedge face structural representation;
Fig. 5 is the structural representation of secondary thrust bearing;
Fig. 6 is that the A-A of Fig. 5 is to view.
embodiment
As shown in Figure 2, Figure 3, Figure 4, split type thrust bearing of turbocharger, it comprises is located at the main thrust bearing of supercharger air compressor end and the secondary thrust bearing near turbine end, and main thrust shaft 2 is located at the end of turbine shaft and is fitted in two end face settings of shaft seal pad with secondary thrust bearing 4 is concentric.
The end face of main thrust bearing 2 is provided with fan-shaped oil film wedge face 7, and the end of oil film wedge face 7 is provided with oil storage tank 3, and oil film wedge face 7 radially outwards forms by the center of circle inclined-plane increasing, circumferentially the inclined-plane for successively decreasing or increasing progressively; Oil film wedge face diameter to outer rim and the end face of main thrust bearing form radially oil sealing limit 7a, the raised limit of oil film wedge face circumferential ramps and the end face of main thrust bearing form circumferential oil sealing limit 7b.
Main thrust bearing has adopted 4 oil film wedge face structures.Increase in order to solve the tile fragment outer edge vent flow that high speed thrust bearing causes due to centrifugal force, the problem that causes bearing capacity to reduce, designed with sealing oil edge tiltedly-the oil film wedge face structure of plane.This inclined-plane has spatial structure, all has varied in thickness at circumference and diametric(al).Inclined-plane peripheral edge portion and plane are contour, form sealing oil edge radially; Inclined-plane side is contour near part and the plane of plane, forms axial monolateral oil sealing.At an oil storage tank of outer rim design processing of oil film wedge face, further improve the storing property of lubricant oil.
As the end face of the secondary thrust bearing of Fig. 5, Fig. 6 is provided with space curved surface oil film wedge face 4a.
Secondary thrust bearing has still adopted 4 oil film wedge face structures with space curved surface, and oil film wedge face is fan-shaped.Oil film wedge face external profile diameter should with the external diameter sizableness of gasket, can increase as far as possible like this oil film loaded area, increase the path of oil film, effectively improve the bearing capacity of secondary thrust bearing.Meanwhile, because intermediate hole wall is to oily rebound effect, can form within the specific limits sealing oil edge, to weaken the radial drainage amount of machine oil.
As shown in Figure 1, the present invention is arranged on turbine shaft 6 ends and coordinates with the installation step of intermediate 1, main thrust bearing 2 outsides are fixed with gland 11, between main thrust bearing 2 and turbine shaft 6, be provided with shaft seal 14, between main thrust bearing 2 and secondary thrust bearing 4, be provided with shaft seal pad 5, turbine shaft 6 ends in intermediate 1 outside are fixed wtih impeller 16 by nut 15, between gland 11 and shaft seal 14, be provided with seal ring 17, the main oil gallery 8 that intermediate 1 is provided with filler opening 9 and is communicated with filler opening, main oil gallery 8 is communicated with the oil groove 10 on main thrust bearing 2, oil groove is communicated with the oil duct 12 of main thrust bearing 2 interior settings, oil duct 12 is being communicated with the oilhole 13 of main thrust bearing 2, the outlet of oilhole 13 is on oil film wedge face 7.
The lubricant oil of two thrust bearings is all by oil duct of intermediate, and main oil gallery directly provides.Lubricant oil passes through successively: oil inlet hole → main oil gallery → oil groove → oil duct → oilhole → oil film wedge face → oil storage tank → oil drainage hole.The oil film wedge face of main thrust bearing and secondary thrust bearing assembles in opposite directions, forms a lubricant reservoir with the endoporus of intermediate.Two oil drain outs of this lubricant reservoir are arranged on the both sides of upper end main oil gallery, can further improve oil pressure.In order further to increase the bearing capacity of main thrust bearing, on four oil film wedge faces, establish respectively special oilhole, outwards supplied with by endoporus, form half hydrostatic bearing.
Main thrust bearing is fixed by the tapped hole on 3 screw holes and intermediate.Pilot hole on the logical interference fit of secondary thrust bearing and intermediate is directly fixing.Shaft seal pad should be less 6～8 than the degree of depth of corresponding aperture on intermediate with secondary thrust bearing thickness sum, to guarantee the forming oil slick thickness of monolateral 3～4 between shaft seal pad and thrust bearing.Meanwhile, the fit up gap of shaft seal pad and thrust bearing need reasonably be designed, and guarantees that the gap between shaft seal pad and thrust bearing is greater than the axial movement value of rotor, to prevent shaft seal pad and thrust bearing generation dry friction.
Claims (2)
1. split type thrust bearing of turbocharger, it comprises is located at the main thrust bearing of supercharger air compressor end and the secondary thrust bearing near turbine end, main thrust bearing is located at the end of turbine shaft and is fitted in two end face settings of shaft seal pad with secondary thrust bearing is concentric, it is characterized in that: the end face of main thrust bearing is provided with fan-shaped oil film wedge face, the end of oil film wedge face is provided with oil storage tank, oil film wedge face diameter, to outwards forming by the center of circle inclined-plane increasing, is circumferentially the inclined-plane that successively decreases or increase progressively; Oil film wedge face diameter to outer rim and the end face of main thrust bearing form radially oil sealing limit, the raised limit of oil film wedge face circumferential ramps and the end face of main thrust bearing form circumferential oil sealing limit.
2. split type thrust bearing of turbocharger according to claim 1, is characterized in that: the end face of described secondary thrust bearing is provided with space curved surface oil film wedge face.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310743167.2A CN103912577A (en) | 2013-12-30 | 2013-12-30 | Split-type turbocharger thrust bearing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310743167.2A CN103912577A (en) | 2013-12-30 | 2013-12-30 | Split-type turbocharger thrust bearing |
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| Publication Number | Publication Date |
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| CN103912577A true CN103912577A (en) | 2014-07-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310743167.2A Pending CN103912577A (en) | 2013-12-30 | 2013-12-30 | Split-type turbocharger thrust bearing |
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| CN (1) | CN103912577A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107654463A (en) * | 2017-11-13 | 2018-02-02 | 中国科学院合肥物质科学研究院 | A kind of container seals Quick locking structure |
| CN109386542A (en) * | 2017-08-04 | 2019-02-26 | 常州环能涡轮动力股份有限公司 | A kind of Turbochargers in Diesel Engines thrust bearing and its installation method |
| CN109424376A (en) * | 2017-08-22 | 2019-03-05 | 通用汽车环球科技运作有限责任公司 | Turbocharger boost bearing |
| WO2019217265A1 (en) * | 2018-05-07 | 2019-11-14 | Borgwarner Inc. | Turbocharger for an internal combustion engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4639148A (en) * | 1984-02-14 | 1987-01-27 | Aisin Seiki Kabushiki Kaisha | Thrust bearing for turbocharger |
| CN1802515A (en) * | 2003-07-05 | 2006-07-12 | 曼·B及W柴油机公开股份有限公司 | Thrust sliding bearing |
| CN101509399A (en) * | 2008-12-18 | 2009-08-19 | 寿光市康跃增压器有限公司 | Split axial carrying device of turbo-charger |
| CN102392697A (en) * | 2011-11-24 | 2012-03-28 | 湖南天雁机械有限责任公司 | Thrust structure for turbocharger |
| WO2013099600A1 (en) * | 2011-12-27 | 2013-07-04 | 三菱重工業株式会社 | Thrust bearing device for supercharger |
| CN203756726U (en) * | 2013-12-30 | 2014-08-06 | 常州环能涡轮动力股份有限公司 | Split-type turbosupercharger thrust bearing |
-
2013
- 2013-12-30 CN CN201310743167.2A patent/CN103912577A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4639148A (en) * | 1984-02-14 | 1987-01-27 | Aisin Seiki Kabushiki Kaisha | Thrust bearing for turbocharger |
| CN1802515A (en) * | 2003-07-05 | 2006-07-12 | 曼·B及W柴油机公开股份有限公司 | Thrust sliding bearing |
| CN101509399A (en) * | 2008-12-18 | 2009-08-19 | 寿光市康跃增压器有限公司 | Split axial carrying device of turbo-charger |
| CN102392697A (en) * | 2011-11-24 | 2012-03-28 | 湖南天雁机械有限责任公司 | Thrust structure for turbocharger |
| WO2013099600A1 (en) * | 2011-12-27 | 2013-07-04 | 三菱重工業株式会社 | Thrust bearing device for supercharger |
| CN203756726U (en) * | 2013-12-30 | 2014-08-06 | 常州环能涡轮动力股份有限公司 | Split-type turbosupercharger thrust bearing |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109386542A (en) * | 2017-08-04 | 2019-02-26 | 常州环能涡轮动力股份有限公司 | A kind of Turbochargers in Diesel Engines thrust bearing and its installation method |
| CN109424376A (en) * | 2017-08-22 | 2019-03-05 | 通用汽车环球科技运作有限责任公司 | Turbocharger boost bearing |
| CN107654463A (en) * | 2017-11-13 | 2018-02-02 | 中国科学院合肥物质科学研究院 | A kind of container seals Quick locking structure |
| CN107654463B (en) * | 2017-11-13 | 2023-09-01 | 中国科学院合肥物质科学研究院 | Quick locking structure of container seal |
| WO2019217265A1 (en) * | 2018-05-07 | 2019-11-14 | Borgwarner Inc. | Turbocharger for an internal combustion engine |
| CN110454430A (en) * | 2018-05-07 | 2019-11-15 | 博格华纳公司 | Internal combustion engine turbocharger |
| US11473447B2 (en) | 2018-05-07 | 2022-10-18 | Borgwarner Inc. | Turbocharger for an internal combustion engine |
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Application publication date: 20140709 |
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| RJ01 | Rejection of invention patent application after publication |